## 4480 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations

(2) Report the results of the inspection required by paragraph (f)(1) of this AD, including no findings, to Airbus, Customer Services Directorate, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex France; Attn: SEDCC1 Technical Data and Documentation Services; Fax (+33) 5 61 93 28 06; e-mail sb.reporting@airbus.com ; at the applicable time specified in paragraph (f)(2)(i) or (f)(2)(ii) of this AD.

(i) If the inspection is done on or after the effective date of this AD: Submit the report within 30 days after the inspection.

(ii) If the inspection was accomplished prior to the effective date of this AD: Submit the report within 30 days after the effective date of this AD.

FAA AD Differences

Note 1: This AD differs from the MCAI and/or service information as follows: No differences.

Other FAA AD Provisions

(g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Vladimir Ulyanov, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1138; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

(3) Reporting Requirements: For any reporting requirement in this AD, under the provisions of the Paperwork Reduction Act (44 U.S.C. 3501 et seq. ), the Office of Management and Budget (OMB) has approved the information collection requirements and has assigned OMB Control Number 2120–0056.

Related Information

(h) Refer to MCAI European Aviation Safety Agency (EASA) Airworthiness Directive 2008–0223, dated December 15, 2008, and the Airbus mandatory service bulletins listed in Table 1 of this AD, for related information.
Material Incorporated by Reference

(i) You must use the service information contained in Table 2 of this AD, as applicable, to do the actions required by this AD, unless the AD specifies otherwise. (1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact Airbus SAS—Airworthiness Office—EAL, 1 Rond Point Maurice Bellonte, 31707 Blagnac Cedex, France; fax +33 5 61 93 45 80; e-mail airworthiness.A330- A340@airbus.com ; Internet http:// www.airbus.com

.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call
425–227–1221 or 425–227–1152.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go
to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_ locations.html

.


### T ABLE 

### 2—M ATERIAL 

### I NCORPORATED
BY 

### R EFERENCE

Airbus Mandatory Service Bulletin— Dated—

A330–32–3220 ............. October 10, 2008. A340–32–4264 ............. October 10, 2008. A340–32–5087 ............. October 10, 2008.

Issued in Renton, Washington, on January 14, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–1277 Filed 1–27–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2009–0912; Directorate Identifier 2009–NM–047–AD; Amendment**  **39–16182; AD 2010–02–11]**

**RIN 2120–AA64**



### Airworthiness Directives; BAE **Systems (Operations) Limited Model BAe 146 and Avro 146–RJ Airplanes** 

**AGENCY** 

### : Federal Aviation Administration (FAA), Department of Transportation (DOT).

**ACTION** 

### : Final rule.

**SUMMARY** 

### : We are adopting a new airworthiness directive (AD) for the products listed above. This AD results from mandatory continuing airworthiness information (MCAI) originated by an aviation authority of another country to identify and correct an unsafe condition on an aviation product. The MCAI describes the unsafe condition as:

Reports have been received of finding corrosion at the Frame 29 wing-to-fuselage attachment lug plate joint. This condition, if not detected and corrected, could result in a degradation of the structural integrity of Frame 29 and the wing-to-fuselage attachment.


### * * * * * The unsafe condition is degradation of the structural integrity of Frame 29 and the wing-to-fuselage attachment, which could result in loss of control of the airplane. We are issuing this AD to require actions to correct the unsafe condition on these products.

**DATES** 

### : This AD becomes effective March 4, 2010.

The Director of the Federal Register approved the incorporation by reference of a certain publication listed in this AD as of March 4, 2010.

**ADDRESSES** 

### : You may examine the AD docket on the Internet at http:// www.regulations.gov or in person at the U.S. Department of Transportation, Docket Operations, M–30, West Building Ground Floor, Room W12–140, 1200 New Jersey Avenue, SE., Washington, DC.

**FOR FURTHER INFORMATION CONTACT** 

### : Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149.

**SUPPLEMENTARY INFORMATION** 

### :

Discussion

We issued a notice of proposed rulemaking (NPRM) to amend 14 CFR part 39 to include an AD that would apply to the specified products. That NPRM was published in the Federal Register on October 19, 2009 (74 FR 53433). That NPRM proposed to correct an unsafe condition for the specified products. The MCAI states:

Reports have been received of finding corrosion at the Frame 29 wing-to-fuselage attachment lug plate joint. This condition, if not detected and corrected, could result in a degradation of the structural integrity of Frame 29 and the wing-to-fuselage attachment.

The current method of inspecting the Frame 29 wing-to-fuselage attachment lug plate joint for corrosion is not considered adequate for finding corrosion in this particular area.

To address this concern, BAE Systems (Operations) Limited has published Inspection Service Bulletin ISB.53–213, which replaces current Maintenance Review Board Report Structurally Significant Items Task 53–20–103 (equal to Maintenance


## 4481 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations

Planning Document Tasks 532003–DVI– 10000–1, 532003–DVI–10000–2 and 532003– DVI–10000–3) and Corrosion Prevention and Control Programme Task C53–230–02–01.

For the reason described above, this AD requires repetitive [detailed] inspections of the Frame 29 wing-to-fuselage attachment lug plate joint [for discrepancies, which are corrosion and fatigue cracking of the bolts and fastener bores; degraded, cracked, missing, and poor condition sealant] and repair(s) [which include replacing bolts, contacting BAE Systems for repairinstructions and doing the repair, and reapplying sealant], as necessary. 

### The unsafe condition is degradation of the structural integrity of Frame 29 and the wing-to-fuselage attachment, which could result in loss of control of the airplane. You may obtain further information by examining the MCAI in the AD docket.

Comments

We gave the public the opportunity to participate in developing this AD. We received no comments on the NPRM or on the determination of the cost to the public. Explanation of Changes Made to This AD

We have revised this AD to identify the legal name of the manufacturer as published in the most recent type certificate data sheet for the affected airplane models.

Conclusion

We reviewed the available data, and determined that air safety and the public interest require adopting the AD with the change described previously. We determined that this change will not increase the economic burden on any operator or increase the scope of the AD.

Differences Between This AD and the MCAI or Service Information

We have reviewed the MCAI and related service information and, in general, agree with their substance. But we might have found it necessary to use different words from those in the MCAI to ensure the AD is clear for U.S. operators and is enforceable. In making these changes, we do not intend to differ substantively from the information provided in the MCAI and related service information.

We might also have required different actions in this AD from those in the MCAI in order to follow our FAA policies. Any such differences are highlighted in a NOTE within the AD. Costs of Compliance

We estimate that this AD will affect 1 product of U.S. registry. We alsoestimate that it will take about 12 workhours per product to comply with the basic requirements of this AD. The average labor rate is $80 per work-hour. Based on these figures, we estimate the cost of this AD to the U.S. operator to be $960. Authority for This Rulemaking

Title 49 of the United States Code specifies the FAA’s authority to issue rules on aviation safety. Subtitle I, section 106, describes the authority of the FAA Administrator. ‘‘ Subtitle VII: Aviation Programs, ’’ describes in more detail the scope of the Agency’s authority.

We are issuing this rulemaking under the authority described in ‘‘ Subtitle VII, Part A, Subpart III, Section 44701: General requirements. ’’ Under that section, Congress charges the FAA with promoting safe flight of civil aircraft in air commerce by prescribing regulations for practices, methods, and procedures the Administrator finds necessary for safety in air commerce. This regulation is within the scope of that authority because it addresses an unsafe condition that is likely to exist or develop on products identified in this rulemaking action. Regulatory Findings

We determined that this AD will not have federalism implications under Executive Order 13132. This AD will not have a substantial direct effect on the States, on the relationship between the national government and the States, or on the distribution of power and responsibilities among the various levels of government.

For the reasons discussed above, I certify this AD:

1. Is not a ‘‘ significant regulatory action ’’ under Executive Order 12866;

2. Is not a ‘‘ significant rule ’’ under the DOT Regulatory Policies and Procedures (44 FR 11034, February 26, 1979); and

3. Will not have a significant economic impact, positive or negative, on a substantial number of small entities under the criteria of the Regulatory Flexibility Act.

We prepared a regulatory evaluation of the estimated costs to comply with this AD and placed it in the AD docket. Examining the AD Docket

You may examine the AD docket on the Internet at http:// www.regulations.gov; or in person at the Docket Operations office between 9 a.m. and 5 p.m., Monday through Friday, except Federal holidays. The AD docket contains the NPRM, the regulatory evaluation, any comments received, and other information. The street address for the Docket Operations office (telephone (800) 647–5527) is in the **ADDRESSES** 

### section. Comments will be available in the AD docket shortly after receipt. List of Subjects in 14 CFR Part 39

Air transportation, Aircraft, Aviation safety, Incorporation by reference, Safety. Adoption of the Amendment

■ 

### Accordingly, under the authority delegated to me by the Administrator, the FAA amends 14 CFR part 39 as follows:

**PART 39—AIRWORTHINESS DIRECTIVES** 

■ 

### 1. The authority citation for part 39 continues to read as follows:

Authority: 49 U.S.C. 106(g), 40113, 44701.

**§ 39.13 [Amended]**

■ 

### 2. The FAA amends § 39.13 by adding the following new AD:
2010–02–11 BAE Systems (Operations) Limited: Amendment 39–16182. Docket No. FAA–2009–0912; Directorate Identifier 2009–NM–047–AD.

Effective Date

(a) This airworthiness directive (AD) becomes effective March 4, 2010.

Affected ADs

(b) None.
Applicability

(c) This AD applies to BAE SYSTEMS (Operations) Limited Model BAe 146–100A, –200A, and –300A series airplanes; and BAE SYSTEMS (Operations) Limited Model Avro 146–RJ70A, 146–RJ85A, and 146–RJ100A airplanes; certificated in any category; all serial numbers.
Subject

(d) Air Transport Association (ATA) of America Code 53: Fuselage.

Reason

(e) The mandatory continuing airworthiness information (MCAI) states:

Reports have been received of finding corrosion at the Frame 29 wing-to-fuselage attachment lug plate joint. This condition, if not detected and corrected, could result in a degradation of the structural integrity of Frame 29 and the wing-to-fuselage attachment.

The current method of inspecting the Frame 29 wing-to-fuselage attachment lug plate joint for corrosion is not considered adequate for finding corrosion in this particular area.

To address this concern, BAE Systems (Operations) Limited has published Inspection Service Bulletin ISB.53–213, which replaces current Maintenance Review Board Report Structurally Significant Items Task 53–20–103 (equal to Maintenance Planning Document Tasks 532003–DVI– 10000–1, 532003–DVI–10000–2 and 532003–


## 4482 Federal Register / Vol. 75, No. 18 / Thursday, January 28, 2010 / Rules and Regulations

DVI–10000–3) and Corrosion Prevention and Control Programme Task C53–230–02–01.

For the reason described above, this AD requires repetitive [detailed] inspections of the Frame 29 wing-to-fuselage attachment lug plate joint [for discrepancies, which are corrosion and fatigue cracking of the bolts and fastener bores; degraded, cracked, missing, and poor condition sealant] and repair(s) [which include replacing bolts, contacting BAE Systems for repairinstructions and doing the repair and reapplying sealant], as necessary. The unsafe condition is degradation of thestructural integrity of Frame 29 and the wingto-fuselage attachment, which could result in loss of control of the airplane.
Actions and Compliance

(f) Unless already done, do the following actions.

(1) Within 24 months after the effective date of this AD, do a detailed inspection fordiscrepancies of the frame 29 wing-tofuselage attachment lug plate joint, in accordance with the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.53– 213, dated May 21, 2008.

Note 1: For the purposes of this AD, a detailed inspection is: ‘‘ An intensive examination of a specific item, installation, or assembly to detect damage, failure, or irregularity. Available lighting is normally supplemented with a direct source of good lighting at an intensity deemed appropriate. Inspection aids such as mirror, magnifying lenses, etc., may be necessary. Surface cleaning and elaborate procedures may be required. ’’

(2) Repeat the inspection required by paragraph (f)(1) of this AD thereafter at intervals not to exceed 48 months.

(3) During any inspection required by paragraph (f)(1) or (f)(2) of this AD, if it is not possible to replace a removed bolt with another bolt having the same part number as a replacement item, before further flight, contact BAE SYSTEMS to replace the removed bolt with an alternative bolt and do the approved BAE SYSTEMS repair.

(4) If during any inspection required by paragraph (f)(1) or (f)(2) of this AD, any discrepancy is found, before further flight, repair in accordance with paragraph 2.C. of the Accomplishment Instructions of BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.53–213, dated May 21,
2008.

(5) Although BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.53– 213, dated May 21, 2008, specifies to submit certain information to the manufacturer, this AD does not include that requirement.

FAA AD Differences

Note 2: This AD differs from the MCAI and/or service information as follows: Although BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.53– 213, dated May 21, 2008; and European Aviation Safety Agency (EASA) AD 2009– 0046, dated March 2, 2009; specify to submit certain information to the manufacturer, this AD does not include that requirement. Other FAA AD Provisions (g) The following provisions also apply to this AD:

(1) Alternative Methods of Compliance (AMOCs): The Manager, International Branch, ANM–116, Transport Airplane Directorate, FAA, has the authority to approve AMOCs for this AD, if requested using the procedures found in 14 CFR 39.19. Send information to ATTN: Todd Thompson, Aerospace Engineer, International Branch, ANM–116, Transport Airplane Directorate, FAA, 1601 Lind Avenue, SW., Renton, Washington 98057–3356; telephone (425) 227–1175; fax (425) 227–1149. Before using any approved AMOC on any airplane to which the AMOC applies, notify your principal maintenance inspector (PMI) or principal avionics inspector (PAI), as appropriate, or lacking a principal inspector, your local Flight Standards District Office. The AMOC approval letter must specifically reference this AD.

(2) Airworthy Product: For any requirement in this AD to obtain corrective actions from a manufacturer or other source, use these actions if they are FAA-approved. Corrective actions are considered FAA-approved if they are approved by the State of Design Authority (or their delegated agent). You are required to assure the product is airworthy before it is returned to service.

Related Information

(h) Refer to MCAI EASA Airworthiness Directive 2009–0046, dated March 2, 2009; and BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.53–213, dated May 21, 2008; for related information.
Material Incorporated by Reference

(i) You must use BAE SYSTEMS (Operations) Limited Inspection Service Bulletin ISB.53–213, dated May 21, 2008, to do the actions required by this AD, unless the AD specifies otherwise.

(1) The Director of the Federal Register approved the incorporation by reference of this service information under 5 U.S.C. 552(a) and 1 CFR part 51.

(2) For service information identified in this AD, contact BAE Systems Regional Aircraft, 13850 McLearen Road, Herndon,Virginia 20171; telephone 703–736–1080; email raebusiness@baesystems.com; Internet http://www.baesystems.com/Businesses/ RegionalAircraft/index.htm.

(3) You may review copies of the service information at the FAA, Transport Airplane Directorate, 1601 Lind Avenue, SW., Renton, Washington. For information on the availability of this material at the FAA, call

425–227–1221 or 425–227–1152.

(4) You may also review copies of the service information that is incorporated by reference at the National Archives and Records Administration (NARA). For information on the availability of this material at NARA, call 202–741–6030, or go

to: http://www.archives.gov/federal

_register/ code

_ of

_ federal

_regulations/ ibr

_ locations.html. Issued in Renton, Washington, on January 14, 2010. Ali Bahrami, Manager, Transport Airplane Directorate, Aircraft Certification Service.
[FR Doc. 2010–1283 Filed 1–27–10; 8:45 am]

**BILLING CODE 4910–13–P**



### DEPARTMENT OF TRANSPORTATION

**Federal Aviation Administration**

**14 CFR Part 39**

**[Docket No. FAA–2010–0047; Directorate Identifier 2009–SW–28–AD; Amendment 39–**  **16177; AD 2010–02–07]**

**RIN 2120–AA64**



### Airworthiness Directives; Eurocopter **France Model SE3160, SA315B, SA316B, SA316C, and SA319B**  **Helicopters**

**AGENCY** 

### : Federal Aviation Administration, DOT.

**ACTION** 

### : Final rule; request for
comments.

**SUMMARY** 

### : This amendment supersedes an existing airworthiness directive (AD) for the specified Eurocopter France (Eurocopter) model helicopters. The existing AD requires certain inspections of a main rotor blade (blade) manufactured under a Parts Manufacturer Approval under Supplemental Type Certificate (STC) SH778GL. The AD requires inspecting each affected root end bolt (bolt) and bolt-hole for corrosion or a crack on the blade root end fitting (fitting) or in a bolt-hole. For certain serial-numbered blades, the AD also requires a one-time pull test on each fitting and blade root end doubler (doubler) to detect disbonding. This AD requires certain inspections for voids in any doubler or fitting and for paint cracks along the forward and aft edge of the blade fitting. Also, this AD requires inspecting the blade tip weight housing attachment. This AD also requires replacing unairworthy blades with airworthy blades. This amendment is prompted by reports from the STC holder of disbonds at the fittings, doublers, and the tip weight fitting. The actions specified by this AD are intended to prevent blade failure and subsequent loss of control of the helicopter.

**DATES** 

### : Effective February 12, 2010.

The incorporation by reference of certain publications listed in the regulations is approved by the Director of the Federal Register as of February 12, 2010.